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Turbomachine blade

a turbine blade and blade technology, applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve problems such as harming the efficiency of turbines, and achieve the effect of reducing the static pressure gradient and reducing the volume of gas passing

Active Publication Date: 2010-02-16
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This design reduces the volume of gas passing between the rim and the ring, enhancing turbomachine efficiency by optimizing gas flow and pressure distribution.

Problems solved by technology

Unfortunately, this phenomenon is harmful to the efficiency of the turbine since the gas F does not contribute to rotating the rotor.

Method used

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  • Turbomachine blade
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Examples

Experimental program
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Embodiment Construction

[0019]The blade examples 11 shown in FIGS. 3 to 5 are rotor blades for a high pressure turbine in a turbojet. Each blade 11 presents a root 12 and a free end 13 remote from the root 12. The blade 11 is hollow so as to be capable of being cooled from the inside by cold air. When it is mounted inside a turbojet, the blade 11 is surrounded by a ring 30, as shown in FIG. 4.

[0020]The blade 11 has an aerodynamic profile: it presents a rounded upstream or leading edge 16, and it tapers to its downstream or trailing edge 17. It also has two opposite sides: a convex suction side 14 and a concave pressure side 15.

[0021]The free end 13 of the blade has an end wall 18 extending over the entire end of the blade and from which there projects a rim 19. The rim 19 is made up of two fractions 20 and 21.

[0022]The first fraction 20 goes from the trailing edge 17 and runs along the suction side 14 to a connection zone 22. The connection zone 22 is a zone of the rim 19 situated at the periphery of the e...

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PUM

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Abstract

A turbomachine blade presenting a free end having an end wall from which there projects a rim, the rim including a first fraction starting from the trailing edge of the blade and running along the suction side of the blade to a connection zone, and a second fraction of closed outline connected to the first fraction at the region of the connection zone. The second fraction extends the first fraction, running along the suction side of the blade, along the leading edge of the blade, and then returning to the connection zone.

Description

[0001]The invention relates to a turbomachine blade having a free end with an end wall from which there projects a rim. By way of example, the blade may be a rotor blade in a turbojet turbine or compressor.BACKGROUND OF THE INVENTION[0002]FIGS. 1 and 2 show the free end of a known type of turbine rotor blade 1. At its free end 3, the blade presents an open cavity or bathtub 2 defined by an end wall 8 and a rim 9 of closed outline that projects from the periphery of said end wall. The rim runs along the suction side 4, the leading edge 6, the pressure side 5, and the trailing edge 7 of the blade.[0003]When mounted inside a turbojet, the rotor blades 1 are surrounded by a ring 30, shown in FIG. 2. The rim 9 serves to prevent the end wall 8 from rubbing against the ring 30. In addition, it serves to optimize the clearance J between the free end 3 of the blade and the ring 30 so as to limit gas flow in this region.[0004]The aerodynamic design of a turbine blade requires the distance fro...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F01D5/02F01D11/08
CPCF01D5/20Y02T50/673Y02T50/60
Inventor BOURY, JACQUES AUGUSTE AMEDEEBOTREL, ERWAN DANIEL
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A